CN207363711U - Cooling circuit and corresponding turbine device and turbomachinery for multi wall blade - Google Patents

Abstract

According to an embodiment, the invention relates to a cooling circuit for a multi-wall blade and a corresponding turbo device and turbo machine. The cooling circuit includes: a pressure side cavity having a surface adjacent to the pressure side of the multiwall blade; a suction side cavity having a surface adjacent to the suction side of the multiwall blade; a first leading edge cavity of a surface adjacent to the suction side, the first leading edge cavity being positioned forward of the pressure side cavity and the suction side cavity; and having a A second leading edge cavity of the surface, the second leading edge cavity being positioned forward of the first leading edge cavity.

Description

Cooling circuits for multi-walled blades and corresponding turbomachines and turbomachines

technical field

The present invention relates generally to turbine systems, and more particularly to cooling circuits for multi-wall blades and corresponding turbo equipment and turbo machines.

Background technique

Gas turbine systems are one example of turbomachines that are widely used, such as in the field of power generation. A conventional gas turbine system includes a compressor section, a combustor section, and a turbine section. During operation of a gas turbine system, various components in the system, such as turbine blades, are subjected to high temperature flows, which can lead to component failure. Since high temperature flows generally result in increased performance, efficiency, and power output of gas turbine systems, it is advantageous to cool components subjected to high temperature flows to allow gas turbine systems to operate at elevated temperatures.

Turbine blades typically contain a complex labyrinth of internal cooling channels. Cooling air, such as provided by a compressor of a gas turbine system, may pass through the internal cooling passages to cool the turbine blades.

A multi-wall turbine blade cooling system may include internal near-wall cooling circuits. Such a near-wall cooling circuit may comprise, for example, near-wall cooling channels adjacent to the outer wall of the multi-wall blade. Near wall cooling channels are generally smaller, requiring less cooling flow while still maintaining sufficient velocity for effective cooling. The other generally larger inefficient central channel of a multi-walled blade can be used as a cooling air source and can be used in one or more reuse circuits to collect and redirect "spent" cooling flow for redistribution to lower thermal load areas of multi-walled blades.

Utility model content

A first aspect of the invention provides a cooling circuit for a multi-wall blade, the cooling circuit comprising a pressure side cavity having a surface adjacent to the pressure side of the multi-wall blade; having a surface adjacent to the suction side of the multi-wall blade a suction side cavity of the surface; a first leading edge cavity having a surface adjacent to the pressure side and the suction side of the multiwall blade, the first leading edge cavity being positioned forward of the pressure side cavity and the suction side cavity; And a second leading edge cavity having surfaces adjacent the pressure side and the suction side of the multi-walled blade, the second leading edge cavity being positioned forward of the first leading edge cavity.

The cooling circuit also includes at least one passage for fluidly coupling the first leading edge cavity to the tip of the multi-walled blade.

The cooling circuit further includes at least one membrane hole for fluidly coupling the first leading edge cavity to at least one of the pressure side and the suction side of the multi-wall blade.

The cooling circuit further includes: a flow of cooling air directed into the second leading edge cavity; for directing a first portion of the flow of cooling air from the second leading edge cavity into the pressure side cavity A turning portion inside; a turning portion for directing a second portion of the cooling air flow from the second leading edge cavity into the suction side cavity; a turning portion for directing the first portion of the cooling air flow a diverter for directing a portion of the flow from the pressure side cavity into the first leading edge cavity; and for directing the second portion of the flow of cooling air from the suction side cavity into the first leading edge cavity; A turning portion in the leading edge cavity, the first portion and the second portion of the cooling air flow are recombined into a recombined air flow in the first leading edge cavity.

The cooling circuit further comprises at least one channel, wherein a portion of the recombined air flow is exhausted from the first leading edge cavity through the at least one channel to the tip of the multi-wall blade to provide the multi-wall Film cooling of the tips of the wall blades.

The cooling circuit further comprises at least one membrane hole, wherein a portion of the recombined air flow is exhausted from the first leading edge cavity through the at least one membrane hole to the pressure side and At least one of the suction sides.

wherein the flow of cooling air in the second leading edge cavity and the flow of recombined cooling air in the first leading edge cavity flow through the multiwall blade in a first direction, and wherein the The first portion and the second portion of the flow of cooling air flow through the multi-wall blade in a second direction.

Wherein said first direction is radially outward through said multi-wall blade, and wherein said second direction is radially inward through said multi-wall blade.

Wherein said first direction is radially inward through said multi-wall blade, and wherein said second direction is radially outward through said multi-wall blade.

Wherein, the multi-walled blade further comprises a central cavity separating the pressure side cavity from the suction side cavity.

A second aspect of the utility model provides a turbine apparatus (turbine apparatus), which includes: a multi-wall turbine blade; and a cooling circuit arranged in the multi-wall turbine blade, the cooling circuit includes: having a pressure a pressure side cavity having a surface adjacent to the suction side of the multi-wall blade; a suction side cavity having a surface adjacent to the suction side of the multi-wall blade; a first leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multi-wall blade cavities, a first leading edge cavity positioned forward of the pressure side cavity and the suction side cavity; and a second leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multiwall blade, the second leading edge cavity The cavity is positioned forward of the first leading edge cavity.

Wherein, the cooling circuit further comprises at least one channel for fluidly coupling the first leading edge cavity to the tip of the multi-walled blade.

Wherein the cooling circuit further comprises at least one membrane hole for fluidly coupling the first leading edge cavity to at least one of the pressure side and the suction side of the multi-wall blade.

Wherein, the cooling circuit further comprises: a cooling air flow introduced into the second leading edge cavity; a diverter in the cavity; a diverter for directing a second portion of the cooling airflow from the second leading edge cavity into the suction side cavity; a diverter for diverting the cooling airflow into the suction side cavity; a first portion directed from the pressure side cavity into the first lip cavity; and a diverter for directing the second portion of the cooling air flow from the suction side cavity into the first leading edge cavity; A turn in the leading edge cavity, the first portion and the second portion of the cooling air flow are recombined into a recombined air flow in the first leading edge cavity.

Wherein, the cooling circuit further comprises at least one channel, wherein a part of the recombined air flow is discharged from the first leading edge cavity through the at least one channel to the tip of the multi-walled blade to provide the Film cooling of the tip of the multi-walled blade.

wherein said cooling circuit further comprises at least one membrane hole, wherein a portion of said recombined air flow is discharged from said first leading edge cavity through said at least one membrane hole to said pressure side of said multi-walled blade and at least one of said suction sides.

wherein the flow of cooling air in the second leading edge cavity and the flow of recombined cooling air in the first leading edge cavity flow through the multiwall blade in a first direction, and wherein the The first portion and the second portion of the flow of cooling air flow through the multi-wall blade in a second direction.

Wherein said first direction is radially outward through said multi-wall blade, and wherein said second direction is radially inward through said multi-wall blade.

Wherein said first direction is radially inward through said multi-wall blade, and wherein said second direction is radially outward through said multi-wall blade.

A third aspect of the present invention provides a turbomachinery comprising: a gas turbine system comprising a compressor component, a combustor component and a turbine component comprising a plurality of turbine blades, and wherein at least one of the turbine blades comprises a multi-wall blade; and a cooling circuit disposed within the multi-wall blade, the cooling circuit comprising: a pressure side cavity having a surface adjacent to the pressure side of the multi-wall blade; having a surface adjacent to the suction side of the multi-wall blade a suction side cavity; a first leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multiwall blade, the first leading edge cavity being positioned forward of the pressure side cavity and the suction side cavity; and having A second leading edge cavity of the surface adjacent the pressure side and the suction side of the multi-walled blade, the second leading edge cavity being positioned forward of the first leading edge cavity.

Exemplary aspects of the present invention solve the problems described in this disclosure and/or other problems not discussed.

Description of drawings

These and other features of the invention will be more readily understood from the following detailed description of various aspects of the invention taken in conjunction with the accompanying drawings depicting various embodiments of the invention.

Fig. 1 shows a perspective view of a multi-wall blade according to an embodiment.

2 is a cross-sectional view of the multi-wall blade of FIG. 1 , according to various embodiments, taken along line XX in FIG. 1 .

FIG. 3 depicts a portion of the cross-sectional view of FIG. 2 showing a leading edge cooling circuit according to various embodiments.

4 is a perspective view of a leading edge cooling circuit according to various embodiments.

FIG. 5 depicts a portion of the cross-sectional view of FIG. 2 showing a leading edge cooling circuit according to various embodiments.

6 is a schematic diagram of a gas turbine system according to various embodiments.

Note that the drawings of the present invention are not necessarily drawn to scale. The drawings are intended to depict only typical aspects of the invention, and therefore should not be considered as limiting the scope of the invention. In the figures, the same reference numerals denote the same elements between the figures.

Detailed ways

As noted above, the present invention relates generally to turbine systems, and more particularly to cooling circuits for cooling multi-walled blades.

In the drawings (see, eg, FIG. 6), the "A" axis represents the axial orientation. As used herein, the terms "axial" and/or "axially" refer to the relative position/orientation of objects along an axis A, which is substantially parallel to the turbomachinery (specifically the rotor section) axis of rotation. As further used herein, the terms "radial" and/or "radially" refer to the relative position/orientation of an object along axis "r" (see, for example, Figure 1), which is substantially vertical is on axis A and intersects axis A at only one location. Additionally, the terms "circumferentially" and/or "circumferentially" refer to the relative position/orientation of objects along a circumference (c) that encloses axis A but does not intersect axis A at any location.

Turning to FIG. 1 , a perspective view of a turbomachine blade 2 is shown. Turbomachine blade 2 includes a shank 4 and a multi-wall blade 6 coupled to and extending radially outward from shank 4 . The multi-wall blade 6 includes a pressure side 8 , an opposite suction side 10 and a tip region 38 . The multiwall blade 6 also comprises a leading edge 14 between the pressure side 8 and the suction side 10 and a trailing edge between the pressure side 8 and the suction side 10 on the side opposite the leading edge 14 )16. The multi-wall blade 6 extends radially away from the platform 3 comprising a pressure side platform 5 and a suction side platform 7 .

Shank 4 and multi-wall blade 6 may each be formed from one or more metals (eg, nickel, nickel alloys, etc.), and may be formed according to conventional methods (eg, casting, forging, or machining). The shank 4 and multi-wall blade 6 may be integrally formed (eg, cast, forged, three-dimensionally printed, etc.), or may be formed as separate components that are subsequently joined (eg, via welding, brazing, bonding, or other coupling mechanism). The multi-walled blades 6 may be fixed blades (nozzles) or rotatable blades.

FIG. 2 depicts a cross-sectional view of the multi-wall blade 6 taken along the line X--X of FIG. 1 . As shown, the multi-wall blade 6 may include a plurality of internal cavities. In an embodiment, the multi-wall blade 6 comprises a plurality of leading edge cavities 18A, 18B, a plurality of pressure side (outer) cavities 20A20D, a plurality of suction side (outer) cavities 22A-22E, a plurality of trailing edge cavities 24A-24C and a plurality of central cavities 26A, 26B. Leading edge cavity 18B is aft of leading edge cavity 18A (closer to trailing edge 16 ). Of course, the number of cavities 18 , 20 , 22 , 24 , 26 within the multiwall blade 6 may vary depending on, for example, the particular configuration, size, intended application, etc. of the multiwall blade 6 . To this extent, the number of cavities 18, 20, 22, 24, 26 shown in the disclosed embodiments of the present invention is not intended to be limiting. Depending on the embodiment, individual cooling circuits may be provided with different combinations of cavities 18 , 20 , 22 , 24 , 26 .

A serpentine leading edge cooling circuit 30 according to an embodiment is depicted in FIGS. 3 and 4 . As the name suggests, the leading edge cooling circuit 30 is positioned adjacent the leading edge 14 of the multiwall blade 6 between the pressure side 8 and the suction side 10 of the multiwall blade 6 .

Referring to FIGS. 3 and 4 concurrently, a cooling air flow 32 generated, for example, by compressor 104 ( FIG. 6 ) of gas turbine system 102 is fed through shank 4 ( FIG. 1 ) to leading edge cooling circuit 30 (e.g., via at least one cooling air supply (feed)). Cooling air flow 32 is supplied to base 34 of leading edge cavity 18A. Cooling air flow 32 flows radially outward through leading edge cavity 18A towards tip region 38 of multi-wall blade 6 , providing convection cooling.

A turn 36 directs a first portion 40 of the cooling airflow 32 from the leading edge cavity 18A into the pressure side cavity 20A. A first portion 40 of the cooling air flow 32 flows radially inwardly through the pressure side cavity 20A, providing convective cooling. Diverter 42 directs a second portion 44 of cooling airflow 32 from leading edge cavity 18A into suction side cavity 22A. A second portion 44 of the cooling airflow 32 flows radially inwardly through the suction side cavity 22A, providing convective cooling. As shown in FIG. 3 , the pressure side cavity 20A includes a surface 46 adjacent the pressure side 8 of the multi-walled blade 6 and a surface 48 adjacent the central cavity 26A. Furthermore, the suction side cavity 22A comprises a surface 50 adjacent to the suction side 10 of the multi-walled blade 6 and a surface 52 adjacent to the central cavity 26A. According to an embodiment, the central cavity 26A is effectively adiabatic, has little or no fluid velocity, and does not have any surfaces adjacent to the pressure side 8 or the suction side 10 of the multiwall blade 6 . Depending on the embodiment, diversions 36, 42 (and other diversions as described below) may include conduits, tubes, pipes, channels and/or allow air or any other gas to flow from Any other suitable mechanism for traveling from one location to another within the multi-walled blade 6 .

The diversion 54 redirects the first portion 40 of the cooling airflow 32 into the base 58 of the leading edge cavity 18B. Similarly, a diverter (not shown) redirects the second portion 44 of the cooling airflow 32 into the base 58 of the leading edge cavity 18B. The first portion 40 and the second portion 44 of the cooling air flow 32 are recombined in the leading edge cavity 18B to reform the cooling flow 32 which passes through the leading edge cavity 18B radially toward the tip region 38 of the multiwall blade 6 . External flow provides convective cooling. As shown in FIG. 3 , the leading edge cavity 18B has a surface 60 adjacent to the pressure side 8 of the multi-wall blade 6 and a surface 62 adjacent to the suction side 10 of the multi-wall blade 6 .

A portion 64 of the cooling air flow 32 may be directed from the leading edge cavity 18B through at least one passage 66 to a tip 68 of the multiwall blade 6 ( FIG. 1 ) as the cooling air flow passes radially outward through the leading edge cavity 18B. The portion 64 of the cooling air flow 32 may exit the tip 68 of the multi-wall blade through at least one channel 66 as a tip film 70 to provide tip film cooling. A further portion 72 of the cooling air flow 32 may exit through one or more apertures 74 in the pressure side 8 and/or suction side 10 of the multiwall blade to provide a cooling film flow on the exterior of the multiwall blade 6 . In other embodiments, said portions 64, 72 of the cooling air flow 32 or other portions of the cooling air flow 32 may be directed to the tip 68 or a cooling circuit in the platform 3 (or inner/outer sidewall), and/or It can be reused in other cooling circuits aft of the meandering leading edge cooling circuit 30 .

As depicted in Figure 5, in other embodiments, the flow direction may be reversed. For example, in FIG. 5 , cooling air flow 132 may be fed into leading edge cavity 18A and flow radially inward through leading edge cavity 18A. Cooling air flow 132 is divided into portions 140 , 144 which are directed into pressure side cavity 20A and suction side cavity 22A, respectively. The portions 140 , 144 of the cooling airflow 132 flow radially outward through the pressure side cavity 20A and the suction side cavity 22A, respectively, and recombine into the resulting airflow 132 in the leading edge cavity 18B. Airflow 132 is then directed radially inward through leading edge cavity 18B. As a portion 164 of cooling air flow 32 passes through leading edge cavity 18B, the portion 164 of cooling air flow 32 may be directed from leading edge cavity 18B to tip 68 of multiwall blade 6 ( FIG. 1 ) through at least one passage 166 . The portion 164 of the cooling air flow 132 may exit the tip 68 of the multi-wall blade 6 through at least one channel 66 as a tip film 70 ( FIG. 1 ) to provide tip film cooling. A portion 172 of the cooling air flow 132 may be used to provide a cooling film flow on the exterior of the multi-wall blade 6 . In other embodiments, said portions 164, 172 of the cooling air flow 132, or other portions of the cooling air flow 132, may be passed to the platform 3 (or inner/outer sidewalls), and/or may be used for a meandering front In other cooling circuits at the rear of edge cooling circuit 130.

The cooling circuit 30, 130 has been illustrated for use in a multi-walled blade 6 of a turbine blade 2 that rotates during operation of the gas turbine. However, the cooling circuit 30, 130 may also be used for cooling within a stationary turbine nozzle of a gas turbine. Additionally, the cooling circuit 30, 130 may be used to cool other structures that require internal cooling air flow during operation.

FIG. 6 shows a schematic view of a gas turbine 102 as may be used in the present invention. Gas turbine 102 may include a compressor 104 . Compressor 104 compresses incoming air stream 106 . Compressor 104 delivers compressed air stream 108 to combustor 110 . Combustor 110 mixes compressed air stream 108 with pressurized fuel stream 112 and ignites the mixture to form combustion gas stream 114 . Although only a single combustor 110 is shown, the gas turbine system 102 may include any number of combustors 110 . Combustion gas stream 114 is then channeled to turbine 116 , which generally includes a plurality of turbomachine blades 2 ( FIG. 1 ). The flow of combustion gases 114 drives a turbine 116 to produce mechanical work. Mechanical work generated in turbine 116 drives compressor 104 via shaft 118 and may be used to drive an external load 120 , such as a generator and/or the like.

In various embodiments, described components described as "coupled" to each other may be coupled along one or more interfaces. In some embodiments, these interfaces may include joints between different components, and in other cases, these interfaces may include rigidly and/or integrally formed interconnections. That is, in some cases, components that are "coupled" to each other may be formed concurrently to define a single continuous member. In other embodiments, however, these coupling components may be formed as separate components and subsequently joined by known processes (eg fastening, ultrasonic welding, gluing).

When an element or layer is referred to as being "on," "joined to," "connected to," or "coupled to" another element, it can be directly on, bonded, connected, or coupled to the other element. One element, or there may be intermediate elements. In contrast, when an element is referred to as being "directly on," "directly engaged to," "directly connected to" or "directly coupled to" another element, there may be no intervening elements or layers present. Other words used to describe the relationship between elements should be interpreted in the same manner (e.g., "between" vs. "directly between", "adjacent to" vs. "directly adjacent to", etc. Wait). As used in this application, the term "and/or" includes any and all combinations of one or more of the associated listed items.

The terms used in the present invention are for the purpose of describing specific embodiments only, and are not intended to limit the present invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprising" and/or "comprising" when used in this specification specify the presence of stated features, integers, steps, operations, elements and/or parts, but do not exclude one or more other The presence or addition of features, integers, steps, operations, elements, parts and/or groups thereof.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims. Inside.

Claims (20)

1. A cooling circuit for a multi-wall blade comprising: a pressure side cavity having a surface adjacent to the pressure side of the multi-walled blade; a suction side cavity having a surface adjacent to the suction side of the multi-walled blade; A first leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multiwall blade, the first leading edge cavity positioned at the pressure the side cavity and the front of the suction side cavity; and A second leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multi-wall blade, the second leading edge cavity positioned on the first A front of the leading edge cavity. 2. The cooling circuit of claim 1, further comprising at least one passage for fluidly coupling the first leading edge cavity to a tip of the multi-walled blade. 3. The cooling circuit of claim 1 , further comprising a valve for fluidly coupling the first leading edge cavity to one of the pressure side and the suction side of the multi-wall blade. at least one of at least one membrane aperture. 4. The cooling circuit according to claim 1, further comprising: a flow of cooling air directed into said second leading edge cavity; a diverter for directing a first portion of the flow of cooling air from the second leading edge cavity into the pressure side cavity; a diverter for directing a second portion of the flow of cooling air from the second leading edge cavity into the suction side cavity; a diverter for directing the first portion of the flow of cooling air from the pressure side cavity into the first leading edge cavity; and A diversion for directing the second portion of the cooling air flow from the suction side cavity into the first leading edge cavity, the first portion of the cooling air flow and the second Portions are recombined into a recombined air flow in said first leading edge cavity. 5. The cooling circuit of claim 4, further comprising at least one channel, wherein a portion of the recombined air flow is exhausted from the first leading edge cavity through the at least one channel to the a tip of the multi-wall blade to provide film cooling of the tip of the multi-wall blade. 6. The cooling circuit of claim 4, further comprising at least one membrane hole, wherein a portion of the recombined air flow is exhausted from the first leading edge cavity through the at least one membrane hole to At least one of the pressure side and the suction side of the multiwall blade. 7. The cooling circuit of claim 4, wherein the flow of cooling air in the second leading edge cavity and the flow of recombined cooling air in the first leading edge cavity travel along a second leading edge cavity. A direction flows through the multi-wall blade, and wherein the first portion and the second portion of the cooling air flow flow through the multi-wall blade in a second direction. 8. The cooling circuit of claim 7, wherein the first direction is radially outward through the multi-wall vane, and wherein the second direction is radially outward through the multi-wall vane inward. 9. The cooling circuit of claim 7, wherein the first direction is radially inward through the multi-wall vane, and wherein the second direction is radially inward through the multi-wall vane outward. 10. The cooling circuit of claim 7, wherein the multi-wall blade further comprises a central cavity separating the pressure side cavity from the suction side cavity. 11. A turbine device comprising: multi-walled turbine blades; and a cooling circuit disposed within the multi-wall turbine blade, the cooling circuit comprising: a pressure side cavity having a surface adjacent to the pressure side of the multi-walled blade; a suction side cavity having a surface adjacent to the suction side of the multi-walled blade; A first leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multiwall blade, the first leading edge cavity positioned at the pressure the side cavity and the front of said suction side cavity; and A second leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multi-wall blade, the second leading edge cavity positioned on the first A front of the leading edge cavity. 12. The turbine apparatus of claim 11, wherein the cooling circuit further comprises at least one channel for fluidly coupling the first leading edge cavity to a tip of the multi-walled blade. 13. The turbine apparatus of claim 11, wherein said cooling circuit further comprises said pressure side and said At least one membrane hole of at least one of the suction sides. 14. The turbine apparatus of claim 11, wherein the cooling circuit further comprises: a flow of cooling air directed into said second leading edge cavity; a diverter for directing a first portion of the flow of cooling air from the second leading edge cavity into the pressure side cavity; a diverter for directing a second portion of the flow of cooling air from the second leading edge cavity into the suction side cavity; a diverter for directing the first portion of the flow of cooling air from the pressure side cavity into the first leading edge cavity; and A diversion for directing the second portion of the cooling air flow from the suction side cavity into the first leading edge cavity, the first portion of the cooling air flow and the second Portions are recombined into a recombined air flow in said first leading edge cavity. 15. The turbine apparatus of claim 14, wherein the cooling circuit further comprises at least one passage, wherein a portion of the reformulated air flow passes from the first leading edge cavity through the at least one passage Expelling to the tip of the multi-wall blade to provide film cooling of the tip of the multi-wall blade. 16. The turbine apparatus of claim 14, wherein the cooling circuit further comprises at least one membrane hole, wherein a portion of the recombined air flow passes from the first leading edge cavity through the at least one Membrane holes exit to at least one of the pressure side and the suction side of the multiwall blade. 17. The turbine apparatus of claim 14, wherein the flow of cooling air in the second leading edge cavity and the flow of recombined cooling air in the first leading edge cavity A direction flows through the multi-wall blade, and wherein the first portion and the second portion of the cooling air flow flow through the multi-wall blade in a second direction. 18. The turbine apparatus of claim 17, wherein the first direction is radially outward through the multi-wall blade, and wherein the second direction is radially outward through the multi-wall blade inward. 19. The turbine apparatus of claim 17, wherein the first direction is radially inward through the multi-wall blade, and wherein the second direction is radially inward through the multi-wall blade outward. 20. A turbomachine comprising: a gas turbine system comprising a compressor component, a combustor component, and a turbine component comprising a plurality of turbine blades, and wherein at least one of the turbine blades comprises a multi-wall blade; and a cooling circuit arranged within the multi-wall blade, the cooling circuit comprising: a pressure side cavity having a surface adjacent to the pressure side of the multi-walled blade; a suction side cavity having a surface adjacent to the suction side of the multi-walled blade; A first leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multiwall blade, the first leading edge cavity positioned at the pressure the side cavity and the front of said suction side cavity; and A second leading edge cavity having surfaces adjacent to the pressure side and the suction side of the multi-wall blade, the second leading edge cavity positioned on the first A front of the leading edge cavity.